阅读说明：本技术 一种极寒地区的火箭保温防护装置 (Rocket heat preservation protector in extremely cold region ) 是由 郭全全 勾永宝 王泽易 于 2019-10-21 设计创作，主要内容包括：本发明公开了一种可快速撤收的火箭保温防护装置及方法,包括可开合桁架筒、动力装置、滑轨和发热保温装置；在筒的立面设置了铰链和开口,从而实现了其开合功能；动力装置为桁架筒的撤收提供动力；滑轨为固定于底面的工字型钢轨,滑轨除为桁架筒撤收提供便利外,还可通过滑轮装置实现桁架筒的抗拔,从而实现了风载下的桁架筒稳定；采用本发明的防护装置施工速度快,可迅速完成完成极寒天气下的火箭装配；并可实现迅速的撤除,缩短火箭发射准备时间。(The invention discloses a rocket heat-insulation protection device capable of being quickly retracted and a method, comprising an openable truss barrel, a power device, a slide rail and a heating and heat-insulation device; the vertical surface of the cylinder is provided with a hinge and an opening, thereby realizing the opening and closing function of the cylinder; the power device provides power for withdrawing the truss barrel; the sliding rail is an I-shaped steel rail fixed on the bottom surface, the sliding rail can facilitate the withdrawing of the truss barrel, and the pulling resistance of the truss barrel can be realized through the pulley device, so that the stability of the truss barrel under wind load is realized; the protection device has high construction speed, and can quickly finish rocket assembly in extremely cold weather; and can realize rapid removal and shorten the preparation time for rocket launching.)

1. A rocket heat preservation protection device capable of being quickly retracted comprises an openable truss barrel, a power device, a slide rail and a heating and heat preservation device; a hinge and an opening are arranged on the vertical surface of the openable truss barrel so as to realize the opening and closing function of the truss barrel, and a pulley device is arranged at the bottom of the openable truss barrel; the power device provides power for withdrawing the truss barrel; the sliding rail is an I-shaped steel rail fixed on the bottom surface, the sliding rail can facilitate the removal and the collection of the truss barrel, and the pulling resistance of the truss barrel can be realized through the cooperation with the pulley device, so that the stability of the truss barrel under wind load is realized.

2. The apparatus of claim 1, wherein: the truss barrel capable of being opened and closed is formed by welding an I-shaped steel column and an angle steel connecting piece, rotation of the truss barrel is achieved by welding lug plates at web positions of two stand columns and connecting the two stand columns through hinges, rubber materials are attached to the two stand columns at the opening of the truss barrel, accordingly, sealing performance of the barrel is guaranteed, heat dissipation is reduced, the power device is a combination of a hydraulic arm and a mechanical transmission device, and the hydraulic arm achieves opening and closing of a truss through a scissor-twisting type component.

3. The apparatus of claim 1, wherein: the power device is realized by driving the bottom pulley to roll through hydraulic pressure, a motor or cable stretching, and the heating and heat-insulating device comprises a truss outer-coated film material, a heat-insulating material and/or a heating device and is used for preventing wind, insulating heat and heating.

4. The apparatus of claim 3, wherein: the truss outer-wrapping film material is an ethylene-tetrafluoroethylene copolymer (ETFE) film, the heat-insulating material is a heat-insulating coating or a heat-insulating filler, the heat-insulating filler is one or more of aerosol heat-insulating felt, phenolic foam and expanded and vitrified micro-beads, the heating device is a heating blanket, the heat-insulating material is arranged between the film material and the heating device, preferably, a ventilating duct is arranged in the wall of the cylinder, and an air blower connected with the ventilating duct is arranged at the bottom of the transmitting platform and used as the heating device.

5. The apparatus of claim 2, wherein: the middle part of the truss barrel is provided with a 'scissors-type' connecting device, the whole structure can be driven to open and close through the extension of the hydraulic arms, when the rocket needs to be launched, the truss structure is opened through the extension of the first hydraulic arm through the 'scissors-type' transmission device, and then the second hydraulic arm contracts to pull the whole truss structure to move outwards, so that the structure can be withdrawn.

6. The apparatus of any one of claims 1-5, wherein: the truss barrel is divided into 3 parts to form a semicircular truss and two 1/4 circular trusses, a plurality of pulley devices are respectively arranged at the middle point column of the semicircular truss, the hinge columns of the two 1/4 circular trusses and the column bottom of an opening position, the truss barrel further comprises a track steering device, the bottom of the semicircular truss is fixed in the opening process and serves as an acting point of the other two 1/4 circular trusses, first hydraulic arms on two sides contract to generate a rotating torque to enable the pulleys to slide along the arc-shaped sliding rails, and after the 1/4 circular trusses rotate for 45 degrees, the pulleys reach the position of the track steering device; the motor of the rail steering device rotates to drive the pulley to steer to the straight rail through the sliding rail, so that the change of the sliding direction is realized; and the second hydraulic arm extends along the straight rail direction, the truss barrel integrally moves through the transmission arm and is far away from the rocket main body, and therefore the truss barrel is retracted.

7. The apparatus of claim 6, wherein: the total number of the pulley devices is 5, the pulley devices are respectively arranged on the midpoint column of the semicircular truss, the hinge columns of the two 1/4 circular trusses and the two column bottoms at the opening positions, wherein 3 pulleys on the straight rail use fixed pulleys, and the other 2 pulleys use rotating pulleys.

8. The apparatus of any one of claims 1-5, wherein: the truss barrel is divided into two semi-barrels, pulley devices are respectively arranged at the hinge column, the semi-circle midpoint column and the column bottom of the opening position, 5 pulley devices and 5 sliding rails are used together, the pulley devices are all rotating pulleys, in the opening process, the first hydraulic arm contracts to generate rotating torque to enable the pulleys to slide along the arc-shaped sliding rails, and the two semi-barrel trusses are respectively driven by the rotating pulleys to rotate to the straight rails; then under the drive of the second hydraulic arm, the truss barrel integrally moves and is far away from the rocket main body, so that the truss barrel is retracted.

9. The apparatus of claims 1-5, wherein: a truss section of thick bamboo passes through the post lower pulley group and is connected with the guide rail, realizes a truss section of thick bamboo resistance to plucking, and its concrete structure is: the I-shaped rail is fixed on a concrete slab through a buckle, a main wheel slides along a sliding rail in the opening and withdrawing processes, two anti-pulling pulleys are arranged in the I-shaped rail to offset vertical pulling force caused by lateral force in the movement process of a part of truss and ensure stable structure, a bearing is arranged at the upper part of the I-shaped rail, so that the steering of the pulleys is realized, the main wheel bears the dead weight and pressure of a truss main body, the two anti-pulling pulleys can provide wind load pull-out resistance for a truss barrel, a withdrawing hydraulic arm is in an opening state for a long time, and a transmission arm, a support truss and an inclined strut are arranged at the hydraulic arm, so that the hydraulic arm extends outwards to drive the whole truss to withdraw.

10. A method of using the apparatus of any one of claims 1 to 9, wherein when the rocket is to be launched, the first hydraulic arm is extended by means of a "scissor" type actuator to expand the truss structure, and then the second hydraulic arm is retracted to pull the entire truss structure outwardly, thereby completing the structure withdrawal.

Technical Field

The invention relates to an independent rocket heat-insulation protection device and method, in particular to a rocket heat-insulation protection device and method capable of being quickly retracted and used in extremely cold areas.

Background

The rocket is a complex system integrating nearly thousands of single machines and thousands of large and small components, wherein some composite materials, especially rubber materials for sealing, such as shock absorbers in the rocket fairing, sealing storage tanks and sealing parts in pipelines, look like some small components, and can have a crucial influence on the overall performance of the rocket. These parts and materials are often sensitive to low temperature and are easily damaged and failed under extremely cold conditions. When the rocket is in an extremely low external temperature condition, a special heat preservation protection device needs to be arranged to ensure that the temperature of a microenvironment where the rocket is located is not too low, and meanwhile, the device needs to have the characteristic of rapid withdrawal to realize timely response of rocket launching. The vehicle-mounted missile is often provided with a vertical launching device (Wang Huayu, research on safety protection system of vertical launching device [ D ], 2017, Wuhan engineering university), and the safety protection system mainly comprises a monitoring system and a process protection device, and the protection device is formed by a protection cross beam, a protection longitudinal beam and a variable amplitude oil cylinder. The missile launching device plays a role in supporting the missile, meets the preparation conditions before launching, can achieve the aiming precision, can correctly assist the missile to take off, but does not have the function of heat preservation and protection. At present, a rocket heat preservation device for realizing the heat preservation effect is not searched yet, and the field still belongs to the blank.

Disclosure of Invention

The invention provides a rocket heat-preservation protection device and method capable of being quickly retracted aiming at the requirement of rocket heat-preservation protection in extremely cold areas, and fills the blank. The key technical problems to be solved are as follows:

1) the material of the heat-insulating layer needs to have the characteristics of air tightness, flame retardance and the like, and the performance is kept stable under the extremely low temperature condition;

2) heating measures are required, and the environment temperature in the heat preservation device can be kept at a higher level when the external environment temperature is lower;

3) the heat-insulating protective device needs to have considerable strength and rigidity in the closing and withdrawing processes so as to resist external wind load;

4) can be quickly withdrawn without influencing rocket launching.

In order to solve the technical problem, the invention designs a rocket heat-insulation protection device capable of being quickly disassembled and folded, which comprises an openable truss barrel, a power device, a slide rail and a heating and heat-insulation device; a hinge and an opening are arranged on the vertical surface of the openable truss barrel so as to realize the opening and closing function of the truss barrel, and a pulley device is arranged at the bottom of the openable truss barrel; the power device provides power for withdrawing the truss barrel; the sliding rail is an I-shaped steel rail fixed on the bottom surface, the sliding rail can facilitate the removal and the collection of the truss barrel, and the pulling resistance of the truss barrel can be realized through the cooperation with the pulley device, so that the stability of the truss barrel under wind load is realized.

The openable truss cylinder is formed by welding an I-shaped steel column and an angle steel connecting piece, and the truss cylinder rotates by welding lug plates at the web positions of two upright posts and connecting the lug plates with hinges. Rubber materials are pasted on the two upright columns at the opening of the truss barrel, so that the sealing performance of the barrel is guaranteed, and the heat dissipation is reduced.

The opening and closing power of the truss barrel can be realized by driving a bottom pulley to roll through hydraulic mechanical transmission, motor or cable stretching. Because the center of gravity of the truss barrel is higher, greater instability exists in the opening and closing and withdrawing processes. In order to ensure the safety, reliability and rapidness of the truss barrel in the opening and closing and withdrawing processes, the power device preferably uses the combination of a hydraulic arm and a mechanical transmission device to provide power for withdrawing the truss barrel; the hydraulic arm realizes the opening and closing of the truss through a 'scissors-twisting' type component.

The heating and heat-insulating device comprises a truss outer coating material, a heat-insulating material and/or a heating device and is used for preventing wind, insulating heat and heating. The truss outer wrapping film material is an ethylene-tetrafluoroethylene copolymer (ETFE) film, the heat insulation material is a heat insulation coating or a heat insulation filler, the heat insulation filler is one or more of an aerosol heat insulation felt, phenolic foam and expanded and vitrified micro bubbles, the heating device is a heating blanket, and the heat insulation material is arranged between the film material and the heating device. In addition, a ventilating duct can be arranged in the cylinder wall, and a blower connected with the ventilating duct is arranged at the bottom of the launching platform to serve as a heating device.

The middle part of the truss barrel is provided with a 'scissors-type' connecting device, the whole structure can be driven to open and close through the extension of the hydraulic arms, when the rocket needs to be launched, the truss structure is opened through the extension of the first hydraulic arm through the 'scissors-type' transmission device, and then the second hydraulic arm contracts to pull the whole truss structure to move outwards, so that the structure can be withdrawn.

The truss cylinder can be divided into two semi-cylinders, pulley devices are respectively arranged at the hinge column, the semi-circle midpoint column and the column bottom of the opening position, 5 pulley devices and 5 sliding rails are used together, the pulley devices are rotating pulleys, in the opening process, the first hydraulic arm contracts to generate rotating torque to enable the pulleys to slide along the arc-shaped sliding rails, and the two semi-cylinder trusses are respectively driven by the rotating pulleys to rotate to the straight rails; then under the drive of the second hydraulic arm, the truss barrel integrally moves and is far away from the rocket main body, so that the truss barrel is retracted.

Preferably, the truss barrel is divided into 3 parts to form a semicircular truss and two 1/4 circular trusses, pulley devices are respectively arranged at a midpoint column of the semicircular truss, hinge columns of the two 1/4 circular trusses and column bottoms of opening positions, the truss barrel totally uses 5 pulley devices, 3 pulleys on a straight rail can be fixed by using a fixed pulley, the other two pulleys use a rotating pulley, opening and withdrawing of the rail can be completed only by laying 3 rails by adding a rail steering device, the bottom of the semicircular truss is fixed in the opening process and serves as acting points of the other two 1/4 circular trusses, hydraulic arms on two sides contract to generate rotating torque to enable the pulleys to slide along the arc-shaped rail, and after the 1/4 circular truss rotates for 45 degrees, the pulleys reach the positions of the sliding rail rotating devices. The motor of the track steering device rotates to drive the pulley to steer the straight rail through the sliding rail, so that the sliding direction is changed, then the hydraulic arm extends along the direction of the straight rail, the truss barrel integrally moves through the transmission arm and is far away from the rocket main body, and the truss barrel is retracted.

A truss section of thick bamboo passes through the post lower pulley group and is connected with the guide rail, realizes a truss section of thick bamboo resistance to plucking, and its concrete structure is: the I-shaped rail is fixed on a concrete slab through a buckle, a main wheel slides along the rail in the opening and withdrawing processes, two anti-pulling pulleys are arranged in the I-shaped rail to counteract vertical pulling force caused by lateral force in the movement process of a part of trusses and guarantee stable structure, and a bearing is arranged at the upper part of the I-shaped rail, so that the steering of the pulleys is realized. The main wheel bears the dead weight and pressure of the truss main body, and the two anti-pulling pulleys can provide wind load anti-pulling force for the truss barrel.

The device is in a closed state for a long time, and the retracting hydraulic arm in the scheme is in an open state for a long time. The long-term exposure of the hydraulic arm causes loss of the hydraulic arm, so that the reliability of the hydraulic arm is reduced, and therefore, a transmission arm, a support truss and a diagonal brace are added at the hydraulic arm. Therefore, the hydraulic arm can extend outwards to drive the whole truss to withdraw.

The invention has the beneficial effects that: a) the truss barrel structure is high in construction speed, and rocket assembly in extremely cold weather can be completed quickly; b) Can realize rapid removal and shorten the preparation time for rocket launching.

Drawings

Fig. 1 is a schematic view of the main structure and mechanical transmission of the present invention.

Fig. 2 is a schematic diagram of the withdrawing process of the present invention.

Figure 3 is a schematic view of the truss barrel bottom pulley of the present invention.

Fig. 4 is a schematic view of the guide rail rotating apparatus of the present invention.

Fig. 5 is a schematic view of the hinge between posts of the present invention.

Fig. 6 is a layout view of the heat-retaining and heating means of the present invention.

In the drawings, like reference numerals are used to designate like elements or structures, wherein: 1-truss barrel, 2-support truss, 3-slide rail, 4-hydraulic arm, 5-driving arm, 6-reinforced connecting beam, 7-track steering device, 8-hinge between columns, 9-rotating bearing, 10-main pulley, 11-anti-pulling pulley, 12-rail fastening device, 13-concrete bottom plate, 14-inclined strut, 15-heating blanket, 16-thermal insulation material, 17-windproof membrane material and 18-rocket.

Detailed Description